CN116266237A - Supersonic near-earth parallel interstage separation method with tail constraint characteristic - Google Patents
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Abstract
The invention provides a supersonic near-earth parallel interstage separation method with tail constraint characteristics, which comprises the following steps: s10, modeling a ground boosting stage and aircraft combination to obtain a combined model of the ground boosting stage and the aircraft; s20, acquiring a flow field at the initial moment of separation movement of the ground boosting stage and the aircraft; s30, performing first separation of the ground boosting stage and the aircraft; s40, performing rigid body motion on the aircraft; s50, performing secondary separation of the ground boosting stage and the aircraft; s60, enabling the aircraft to perform six-freedom movement around the mass center; s70, acquiring attitude information, stress information and position information of the aircraft in the second separation process; s80, judging whether the aircraft meets the safety separation requirement, if so, completing separation of the aircraft and the ground boosting stage; otherwise, the angle of attack of the aircraft is adjusted and the flow goes to S10. The invention can solve the technical problems that the separation method in the prior art is not suitable for near-ground parallel interstage separation and cannot realize safe separation.
Description
Technical Field
The invention relates to the technical field of electromagnetic boosting emission near-ground supersonic interstage separation, in particular to a supersonic near-ground parallel interstage separation method with tail constraint characteristics.
Background
The electromagnetic emission is to utilize electromagnetic force to eliminate friction resistance and vibration, and provide strong accelerating ability, accelerate the craft (carrier-borne aircraft/rocket, etc.) to the separation speed near the ground, endow certain initial kinetic energy, have the characteristics of low emission cost, quick response, simple ground facility operation, maintenance, use, low manpower cost, high reliability, etc., and is an important technical approach of the future electromagnetic emission, and has wide application prospect.
Electromagnetic emission is mainly divided into parallel type and serial type according to the positional relationship between the aircraft and the sledge car in charge of carrying the aircraft. In either form, the combination of skid and aircraft presents a complex flow unsteady/aerodynamic loading problem during high speed operation near ground. The problems of unsteady flow are studied earlier by the foreign projects such as rocket sled test, electromagnetic ejection and the like. When the speed reaches supersonic speed, a series of shock wave interference phenomena occur between the combined body and the ground, and the interference structure is greatly influenced by the relative position/speed/acceleration of the combined body and the ground. Thus, the aircraft-boost stage exhibits significant unsteady aerodynamic characteristics during near-ground separation. Meanwhile, the near-ground dynamic pressure environment is worse than the traditional flight environment of the aircraft, so that the load of the aircraft is extremely easy to overrun, and the aircraft is easy to disassemble. The above problems have a significant impact on the safe separation of near-ground supersonic speeds.
In the existing separation mode, the separation mode mainly comprises active separation mode and passive separation mode. Catapulting is typically active. Such as externally hung catapulting, externally hung guide rails, gravity throwing type, submerged catapulting and steam electromagnetic catapulting are commonly used for airborne, high-altitude, light or low-speed objects such as air-to-air missiles, carrier-based aircraft catapulting and the like. Passive separation is mainly represented by pneumatic free separation by means of aerodynamic force difference of its own components. Such as projectile/sabot separation, rocket stage separation, fairing two-lobe translational separation, etc. Active/passive separation is employed in serial/parallel environments to varying degrees.
The ejection type device is mainly suitable for low-speed, light and high-speed high altitude, and is not suitable for ground-near high-speed heavy-load separation. The adoption of catapulting separation presents great challenges for the vertical structural strength of the ground boosting stage/the aircraft and the performance of the catapulting, presents safety risks and is hardly realized. In addition, because the catapult has large mass, more electromagnetic thrust is needed to accelerate, and the catapult has strict requirements on catapult performance, so that the catapult has the economic negative benefits of high research and development cost, long development period and the like.
Passive free separation requires accurate computational evaluation of the trajectories during separation. The accuracy degree of aerodynamic force determines the separation safety margin, but a larger unsteady phenomenon exists in the near-earth stage, accurate estimation under any moment state can not be given, and a larger separation failure risk exists. Meanwhile, as the separation moment is too large, the head lifting speed of the separation body is too high, and the vertical overload overrun is easily caused by the collision of the tail and the rapid increase of the attack angle.
Disclosure of Invention
In order to solve the technical problems, the invention provides a supersonic near-ground parallel interstage separation method with tail constraint characteristics, which can solve the technical problems that the separation method in the prior art is not suitable for near-ground parallel interstage separation and cannot realize safe separation.
According to an aspect of the invention, there is provided a supersonic near-earth parallel interstage separation method with tail constraint characteristics, the method comprising:
s10, modeling a ground boosting stage and aircraft combination to obtain a combined model of the ground boosting stage and the aircraft;
s20, acquiring a flow field at the initial moment of separation movement of the ground boosting stage and the aircraft based on a combined model of the ground boosting stage and the aircraft;
s30, on the basis of a flow field at the initial moment of separation movement, completely unlocking a head locking device in a combined model of the ground boosting stage and the aircraft, and partially unlocking a tail locking device so as to reserve partial constraint of the tail locking device on the aircraft, thereby realizing the first separation of the ground boosting stage and the aircraft;
s40, the aircraft performs rigid motion around the tail locking device under the action of self aerodynamic force, and simultaneously, the ground boosting stage performs braking and deceleration;
s50, under the condition that the acting force of the aircraft on the tail locking device is changed from pressure to zero or from pressure to a preset tension value, the tail locking device in the combined model of the ground boosting stage and the aircraft is completely unlocked, so that the ground boosting stage is completely separated from the aircraft, and the ground boosting stage is separated from the aircraft for the second time;
s60, the aircraft moves around the mass center in six degrees of freedom under the action of self aerodynamic force, self gravity and aerodynamic interference force of the ground boosting stage;
s70, acquiring attitude information, stress information and position information of the aircraft in the second separation process;
s80, judging whether the aircraft meets the safety separation requirement or not based on the attitude information, the stress information and the position information of the aircraft in the second separation process, and if so, completing separation of the aircraft and the ground boosting stage; otherwise, the angle of attack of the aircraft is adjusted and the flow goes to S10.
Preferably, in S30, on the basis of the flow field at the initial moment of the separation movement, the head locking device in the combined model of the ground boosting stage and the aircraft is completely unlocked, and the tail locking device is partially unlocked so as to reserve the partial constraint of the tail locking device on the aircraft, so that the first separation of the ground boosting stage and the aircraft is realized, including: on the basis of a flow field at the initial moment of separation movement, a head locking device in a combined model of the ground boosting stage and the aircraft is completely unlocked, and a tail locking device is partially unlocked so as to reserve the constraint of the tail locking device on the transverse linear displacement, the longitudinal angular displacement, the vertical linear displacement and the vertical angular displacement of the aircraft, thereby realizing the first separation of the ground boosting stage and the aircraft.
Preferably, in S40, the performing rigid motion of the vehicle about the tail lock under self aerodynamic force includes: the aircraft slides along the longitudinal direction and rotates along the transverse direction under the action of self aerodynamic force.
Preferably, in S20, obtaining the flow field at the initial moment of the separation movement of the ground boosting stage and the aircraft based on the combined model of the ground boosting stage and the aircraft includes:
s21, acquiring a calculation grid of a combined model of the ground boosting stage and the aircraft by utilizing grid generation software;
s22, acquiring a Navier-Stokes equation in a discrete form under a calculation grid by using fluid simulation software;
s23, acquiring a flow field of the ground boosting stage and the initial moment of the separation movement of the aircraft based on a Navier-Stokes equation.
Preferably, in S21, the calculation grid is an overlapped grid, a reconstructed grid or a sliding grid.
Preferably, in S21, the mesh generation software is an ICEM software or a Pointwise software.
Preferably, in S22, the fluid simulation software is Fluent software or starCCM software.
Preferably, in S80, determining whether the aircraft meets the safety separation requirement based on the attitude information, the stress information, and the position information of the aircraft in the second separation process includes:
s81, judging whether a course angle, a pitch angle and a roll angle in the attitude information are respectively smaller than a preset course angle, a preset pitch angle and a preset roll angle;
s82, judging whether the stress value in the stress information is smaller than a preset stress value;
s83, acquiring the separation distance between the aircraft and the ground boosting stage based on the position information, and judging whether the separation distance is smaller than a preset separation safety distance;
s84, if yes, meeting the safety separation requirement; otherwise, the safety separation requirement is not satisfied.
According to another aspect of the present invention there is provided a computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing any of the methods described above when executing the computer program.
By adopting the technical scheme of the invention, the separation is carried out in a twice separation mode, the forced tail constraint is reserved in the first separation, and the tail constraint is released along with the separation process reaching a safer separation environment, so that the safety separation between the aircraft and the ground boosting stage is realized. Compared with the prior art, the invention has the following beneficial effects:
(1) The forced tail constraint avoids the problem of separation collision caused by nonlinear and calculation errors and other potential dangerous factors in the early stage of separation;
(2) The device is particularly beneficial to the situations of small separating force and large separating moment, reasonably and fully utilizes aerodynamic force in the separating process, and has the characteristic of low cost.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 illustrates a flow chart of a supersonic near-earth parallel interstage separation method with tail constraint features provided in accordance with an embodiment of the invention;
FIG. 2 shows a schematic diagram of a combined model of an aircraft and boost stage provided in accordance with an embodiment of the present invention;
FIG. 3 illustrates a partitioning schematic of an overlapping grid provided in accordance with one embodiment of the present invention;
FIG. 4 illustrates a schematic timing diagram of separation of an aircraft from a booster according to one embodiment of the invention;
FIG. 5 illustrates a schematic view of an aircraft stress provided in accordance with an embodiment of the present invention;
fig. 6a shows a pressure profile for separation time t=0.00 s at ma1.8 provided in accordance with an embodiment of the present invention;
fig. 6b shows a pressure profile for separation time t=0.05 s at ma1.8 provided in accordance with an embodiment of the present invention;
fig. 6c shows a pressure profile for separation time t=0.10 s at ma1.8 provided in accordance with an embodiment of the present invention;
fig. 6d shows a pressure profile for separation time t=0.15 s at ma1.8 provided in accordance with an embodiment of the present invention;
fig. 6e shows a pressure profile for separation time t=0.20 s at ma1.8 provided in accordance with an embodiment of the present invention;
fig. 6f shows a pressure profile for separation time t=0.25 s at ma1.8 provided in accordance with an embodiment of the present invention.
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
As shown in fig. 1, the invention provides a supersonic near-earth parallel interstage separation method with tail constraint characteristics, which comprises the following steps:
s10, modeling a ground boosting stage and aircraft combination to obtain a combined model of the ground boosting stage and the aircraft;
s20, acquiring a flow field at the initial moment of separation movement of the ground boosting stage and the aircraft based on a combined model of the ground boosting stage and the aircraft;
s30, on the basis of a flow field at the initial moment of separation movement, completely unlocking a head locking device in a combined model of the ground boosting stage and the aircraft, and partially unlocking a tail locking device so as to reserve partial constraint of the tail locking device on the aircraft, thereby realizing the first separation of the ground boosting stage and the aircraft;
s40, the aircraft performs rigid motion around the tail locking device under the action of self aerodynamic force, and simultaneously, the ground boosting stage performs braking and deceleration;
s50, under the condition that the acting force of the aircraft on the tail locking device is changed from pressure to zero or from pressure to a preset tension value, the tail locking device in the combined model of the ground boosting stage and the aircraft is completely unlocked, so that the ground boosting stage is completely separated from the aircraft, and the ground boosting stage is separated from the aircraft for the second time;
s60, the aircraft moves around the mass center in six degrees of freedom under the action of self aerodynamic force, self gravity and aerodynamic interference force of the ground boosting stage;
s70, acquiring attitude information, stress information and position information of the aircraft in the second separation process;
s80, judging whether the aircraft meets the safety separation requirement or not based on the attitude information, the stress information and the position information of the aircraft in the second separation process, and if so, completing separation of the aircraft and the ground boosting stage; otherwise, the angle of attack of the aircraft is adjusted and the flow goes to S10.
The invention adopts a twice separation mode to carry out separation, and the forced tail constraint is reserved in the first separation, so that the tail constraint is released along with the separation process reaching a safer separation environment, thereby realizing the safe separation between the aircraft and the ground boosting stage. Compared with the prior art, the invention has the following beneficial effects:
(1) The forced tail constraint avoids the problem of separation collision caused by nonlinear and calculation errors and other potential dangerous factors in the early stage of separation;
(2) The device is particularly beneficial to the situations of small separating force and large separating moment, reasonably and fully utilizes aerodynamic force in the separating process, and has the characteristic of low cost.
In the invention, the aircraft is connected with the ground boosting stage in parallel through two locking devices, as shown in fig. 2, the aircraft is arranged above the ground boosting stage, the head of the aircraft is connected with the ground boosting stage through the head locking device, and the tail of the aircraft is connected with the ground boosting stage through the tail locking device.
Wherein, as shown in fig. 2, the x direction is the longitudinal direction of the aircraft, that is, along the movement direction of the guide rail, the y direction is the vertical direction of the aircraft, and the z direction is the transverse direction of the aircraft.
According to one embodiment of the present invention, in S20, acquiring a flow field at an initial moment of separation movement of the ground boost stage from the vehicle based on a combined model of the ground boost stage and the vehicle includes:
s21, acquiring a calculation grid of a combined model of the ground boosting stage and the aircraft by utilizing grid generation software;
wherein, the calculation grid can adopt an overlapped grid, a reconstruction grid or a sliding grid, and the grid generation software can adopt ICEM software or Pointwise software;
s22, acquiring a Navier-Stokes equation in a discrete form under a calculation grid by using fluid simulation software;
wherein, the fluid simulation software can adopt Fluent software or starCCM software;
s23, acquiring a flow field of the ground boosting stage and the initial moment of the separation movement of the aircraft based on a Navier-Stokes equation.
According to one embodiment of the present invention, in S30, on the basis of the flow field at the initial moment of the separation movement, completely unlocking the head locking device in the combined model of the ground boosting stage and the aircraft, and partially unlocking the tail locking device to reserve the partial constraint of the tail locking device on the aircraft, so as to realize the first separation of the ground boosting stage and the aircraft, including: on the basis of a flow field at the initial moment of separation movement, a head locking device in a combined model of the ground boosting stage and the aircraft is completely unlocked, and a tail locking device is partially unlocked so as to reserve the constraint of the tail locking device on the transverse linear displacement, the longitudinal angular displacement, the vertical linear displacement and the vertical angular displacement of the aircraft, thereby realizing the first separation of the ground boosting stage and the aircraft.
Through the arrangement, a safer separation environment is created for the second separation, the problem of separation collision caused by nonlinear, calculation error and other potential dangerous factors in the earlier stage of separation is avoided, and the safety of separation between the aircraft and the ground booster stage is improved.
According to one embodiment of the invention, in S40, the rigid body motion of the vehicle about the tail lock under its own aerodynamic force comprises: the aircraft slides along the longitudinal direction and rotates along the transverse direction under the action of self aerodynamic force.
The aircraft rotates along the transverse direction, so that the aircraft gradually rises under the action of self aerodynamic force, and meanwhile, the lifting force is gradually increased and acts on the tail locking device. The lift force at the initial moment is smaller, the acting force generated by the aircraft on the tail locking device is pressure, and the pressure gradually decreases and becomes a pulling force along with the gradual increase of the lift force, so that the second separation condition is reached at the moment, and the second separation can be performed.
According to one embodiment of the present invention, in S80, determining whether the vehicle meets the safety separation requirement based on the attitude information, the stress information, and the position information of the vehicle in the second separation process includes:
s81, judging whether a course angle, a pitch angle and a roll angle in the attitude information are respectively smaller than a preset course angle, a preset pitch angle and a preset roll angle;
s82, judging whether the stress value in the stress information is smaller than a preset stress value;
s83, acquiring the separation distance between the aircraft and the ground boosting stage based on the position information, and judging whether the separation distance is smaller than a preset separation safety distance;
s84, if yes, meeting the safety separation requirement; otherwise, the safety separation requirement is not satisfied.
For a further understanding of the present invention, the supersonic near-parallel interstage separation method with tail constraint features of the present invention is described in detail below in conjunction with FIGS. 1-6.
In this embodiment, a supersonic near-earth parallel interstage separation method with tail constraint features is provided, the method comprising:
step one, modeling a ground boosting stage and aircraft combination to obtain a combined model of the ground boosting stage and the aircraft, as shown in fig. 2;
step two, acquiring an overlapped grid of a combined model of the ground boosting stage and the aircraft by using ICEM software, as shown in figure 3; utilizing Fluent software to obtain a Navier-Stokes equation in a discrete form under the overlapped grid; acquiring a flow field at the initial moment of separation movement of a ground boosting stage and an aircraft based on a Navier-Stokes equation, wherein a turbulence model of the flow field is a Stanκε model, and boundary conditions are set as follows: the inlet is a Ma1.8 pressure far field, the incoming flow speed is a separation speed, the outlet is a pressure outlet, and the ground is a wall surface without sliding movement;
on the basis of a flow field at the initial moment of separation movement, completely unlocking a head locking device in a combined model of the ground boosting stage and the aircraft, and partially unlocking a tail locking device to reserve the constraint of the tail locking device on transverse linear displacement, longitudinal angular displacement, vertical linear displacement and vertical angular displacement of the aircraft, so that the first separation of the ground boosting stage and the aircraft is realized, wherein the separation time sequence is shown in figure 4;
the control code for the first separation is as follows:
fourthly, the aircraft slides along the longitudinal direction and rotates along the transverse direction under the action of self aerodynamic force, and meanwhile, the ground boosting stage brakes and decelerates;
step five, gradually changing the acting force of the aircraft on the tail locking device from pressure to tension along with the gradual increase of the lifting force of the aircraft, and completely unlocking the tail locking device in the combined model of the ground boosting stage and the aircraft when the tension value reaches 17036N so as to completely separate the ground boosting stage from the aircraft, thereby realizing the second separation of the ground boosting stage and the aircraft;
the control code for the first separation is as follows:
step six, the aircraft moves around the mass center in six free ways under the action of self aerodynamic force, self gravity and aerodynamic interference force of the ground boosting stage;
step seven, acquiring attitude information, stress information and position information of the aircraft in the second separation process, wherein the stress condition of the aircraft is shown in fig. 5; in fig. 5, L denotes aerodynamic lift, D denotes aerodynamic drag, M denotes aerodynamic pitch moment around centroid C, C denotes centroid, fx denotes propulsive force, fy1 denotes first supporting force, and Fy2 denotes second supporting force;
wherein, the dynamic simulation is set as follows: calculating characteristic time
l is the characteristic length, the model length is generally taken, V ∞ Is the separation speed. In the embodiment, the physical iteration time step is 0.0001s, and the inner iteration step number is set to be 20;
and step eight, judging that the aircraft meets the safety separation requirement based on the attitude information, the stress information and the position information of the aircraft in the second separation process, and completing separation of the aircraft and the ground boosting stage.
Fig. 6 shows pressure profiles at different separation moments at ma1.8 provided according to an embodiment of the invention. As can be seen from fig. 6, with ground boosting stage braking, the aircraft is first raised around the aft restraint point, the aircraft angle of attack increases, and lift increases. After t=0.1 s, the tail constraint is released, the aircraft is rapidly far away from the ground boosting stage under the action of a large lifting force, and the safety separation between the aircraft and the ground boosting stage and the supersonic speed ground approaching stage is realized.
The method is applicable to near-ground parallel supersonic electromagnetic boosting separation environments, and the following technical problems can be solved by adopting the method of the invention: firstly, the problem that the quality of a separated object is large is avoided, and the catapulting is easy to produce destructive influence on the aircraft/boosting stage structure; secondly, in the separation process, the pneumatic environment is avoided being bad compared with the traditional separation environment, and the structural damage of the aircraft is easy to cause; thirdly, the situation that the aircraft mainly shows smaller separating force and larger separating moment in the initial stage of near-ground supersonic speed separation is avoided, and collision between the tail of the aircraft and a boosting stage is easy to cause.
The invention also provides a computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing any of the methods described above when executing the computer program.
In summary, the invention provides a supersonic near-earth parallel interstage separation method with tail constraint characteristics, which adopts a twice separation mode to separate, and the forced tail constraint is reserved in the first separation, so that the tail constraint is released along with the separation process reaching a safer separation environment, and the safe separation between an aircraft and a ground booster stage is realized. Compared with the prior art, the invention has the following beneficial effects:
(1) The forced tail constraint avoids the problem of separation collision caused by nonlinear and calculation errors and other potential dangerous factors in the early stage of separation;
(2) The device is particularly beneficial to the situations of small separating force and large separating moment, reasonably and fully utilizes aerodynamic force in the separating process, and has the characteristic of low cost.
In the description of the present invention, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present invention; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A supersonic near-earth parallel interstage separation method with tail constraint features, the method comprising:
s10, modeling a ground boosting stage and aircraft combination to obtain a combined model of the ground boosting stage and the aircraft;
s20, acquiring a flow field at the initial moment of separation movement of the ground boosting stage and the aircraft based on a combined model of the ground boosting stage and the aircraft;
s30, on the basis of a flow field at the initial moment of separation movement, completely unlocking a head locking device in a combined model of the ground boosting stage and the aircraft, and partially unlocking a tail locking device so as to reserve partial constraint of the tail locking device on the aircraft, thereby realizing the first separation of the ground boosting stage and the aircraft;
s40, the aircraft performs rigid motion around the tail locking device under the action of self aerodynamic force, and simultaneously, the ground boosting stage performs braking and deceleration;
s50, under the condition that the acting force of the aircraft on the tail locking device is changed from pressure to zero or from pressure to a preset tension value, the tail locking device in the combined model of the ground boosting stage and the aircraft is completely unlocked, so that the ground boosting stage is completely separated from the aircraft, and the ground boosting stage is separated from the aircraft for the second time;
s60, the aircraft moves around the mass center in six degrees of freedom under the action of self aerodynamic force, self gravity and aerodynamic interference force of the ground boosting stage;
s70, acquiring attitude information, stress information and position information of the aircraft in the second separation process;
s80, judging whether the aircraft meets the safety separation requirement or not based on the attitude information, the stress information and the position information of the aircraft in the second separation process, and if so, completing separation of the aircraft and the ground boosting stage; otherwise, the angle of attack of the aircraft is adjusted and the flow goes to S10.
2. The method of claim 1, wherein in S30, based on the flow field at the initial moment of the separation movement, completely unlocking the head locking device in the combined model of the ground propulsion stage and the vehicle, and partially unlocking the tail locking device to preserve the partial restraint of the tail locking device on the vehicle, thereby achieving the first separation of the ground propulsion stage and the vehicle comprises: on the basis of a flow field at the initial moment of separation movement, a head locking device in a combined model of the ground boosting stage and the aircraft is completely unlocked, and a tail locking device is partially unlocked so as to reserve the constraint of the tail locking device on the transverse linear displacement, the longitudinal angular displacement, the vertical linear displacement and the vertical angular displacement of the aircraft, thereby realizing the first separation of the ground boosting stage and the aircraft.
3. The method of claim 2, wherein in S40, the rigid body motion of the vehicle about the tail lock under its own aerodynamic forces comprises: the aircraft slides along the longitudinal direction and rotates along the transverse direction under the action of self aerodynamic force.
4. The method of claim 1, wherein in S20, obtaining a flow field for an initial moment of separation movement of the ground boost stage from the vehicle based on the combined model of the ground boost stage and the vehicle comprises:
s21, acquiring a calculation grid of a combined model of the ground boosting stage and the aircraft by utilizing grid generation software;
s22, acquiring a Navier-Stokes equation in a discrete form under a calculation grid by using fluid simulation software;
s23, acquiring a flow field of the ground boosting stage and the initial moment of the separation movement of the aircraft based on a Navier-Stokes equation.
5. The method of claim 4, wherein in S21, the calculation grid is an overlapped grid, a reconstructed grid, or a sliding grid.
6. The method according to claim 4 or 5, wherein in S21, the mesh generation software is an ICEM software or a Pointwise software.
7. The method according to any one of claims 4-6, wherein in S22, the fluid simulation software is Fluent software or starCCM software.
8. The method of claim 1, wherein determining whether the vehicle meets the safety separation requirement based on the attitude information, the stress information, and the position information of the vehicle during the second separation in S80 comprises:
s81, judging whether a course angle, a pitch angle and a roll angle in the attitude information are respectively smaller than a preset course angle, a preset pitch angle and a preset roll angle;
s82, judging whether the stress value in the stress information is smaller than a preset stress value;
s83, acquiring the separation distance between the aircraft and the ground boosting stage based on the position information, and judging whether the separation distance is smaller than a preset separation safety distance;
s84, if yes, meeting the safety separation requirement; otherwise, the safety separation requirement is not satisfied.
9. A computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the processor implements the method of any of claims 1 to 8 when executing the computer program.
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